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AH 93-156 (ah93156-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: AH 93-156 (ah93156-il)
Reynolds number: 100,000
Max Cl/Cd: 35.53 at α=10.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ah93156-il-100000-n5.txt
Download as CSV file: xf-ah93156-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 93-156                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.1933   0.10290   0.09738  -0.0968   0.8869   0.0354
 -11.750  -0.1928   0.09847   0.09295  -0.0992   0.8832   0.0350
 -11.500  -0.1943   0.09382   0.08829  -0.1017   0.8797   0.0351
 -11.250  -0.1991   0.08892   0.08343  -0.1042   0.8756   0.0356
 -11.000  -0.2068   0.08342   0.07796  -0.1073   0.8716   0.0360
 -10.750  -0.2171   0.07728   0.07184  -0.1110   0.8677   0.0358
 -10.500  -0.2435   0.06760   0.06216  -0.1180   0.8631   0.0353
 -10.250  -0.2772   0.06052   0.05496  -0.1213   0.8574   0.0344
 -10.000  -0.3048   0.05603   0.05029  -0.1210   0.8524   0.0346
  -9.750  -0.3299   0.05254   0.04660  -0.1186   0.8477   0.0343
  -9.500  -0.3500   0.05014   0.04401  -0.1148   0.8427   0.0346
  -9.250  -0.3635   0.04742   0.04099  -0.1114   0.8385   0.0349
  -9.000  -0.3717   0.04464   0.03785  -0.1082   0.8352   0.0354
  -8.750  -0.3763   0.04218   0.03504  -0.1049   0.8307   0.0358
  -8.500  -0.3758   0.03979   0.03226  -0.1020   0.8269   0.0363
  -8.250  -0.3705   0.03748   0.02948  -0.0994   0.8238   0.0371
  -8.000  -0.3606   0.03547   0.02695  -0.0971   0.8211   0.0385
  -7.750  -0.3440   0.03443   0.02586  -0.0960   0.8184   0.0400
  -7.500  -0.3297   0.03358   0.02487  -0.0944   0.8145   0.0416
  -7.250  -0.3129   0.03237   0.02342  -0.0931   0.8114   0.0433
  -7.000  -0.2931   0.03105   0.02180  -0.0919   0.8088   0.0450
  -6.750  -0.2711   0.02989   0.02035  -0.0911   0.8065   0.0475
  -6.500  -0.2485   0.02904   0.01949  -0.0906   0.8045   0.0501
  -6.250  -0.2303   0.02846   0.01882  -0.0894   0.8009   0.0528
  -6.000  -0.2106   0.02781   0.01801  -0.0882   0.7975   0.0556
  -5.750  -0.1900   0.02715   0.01730  -0.0873   0.7946   0.0593
  -5.500  -0.1682   0.02661   0.01674  -0.0865   0.7921   0.0637
  -5.250  -0.1442   0.02600   0.01598  -0.0858   0.7900   0.0686
  -5.000  -0.1221   0.02542   0.01543  -0.0851   0.7881   0.0747
  -4.750  -0.1110   0.02544   0.01542  -0.0827   0.7832   0.0807
  -4.500  -0.0942   0.02513   0.01514  -0.0811   0.7796   0.0880
  -4.250  -0.0737   0.02477   0.01476  -0.0800   0.7769   0.0990
  -4.000  -0.0513   0.02436   0.01437  -0.0791   0.7747   0.1139
  -3.750  -0.0279   0.02392   0.01400  -0.0785   0.7730   0.1366
  -3.500  -0.0216   0.02414   0.01435  -0.0754   0.7670   0.1594
  -3.250  -0.0050   0.02389   0.01430  -0.0738   0.7634   0.2057
  -3.000   0.0141   0.02337   0.01420  -0.0726   0.7608   0.2932
  -2.750   0.0304   0.02259   0.01403  -0.0706   0.7587   0.4373
  -2.500   0.0848   0.02288   0.01563  -0.0717   0.7583   0.7596
  -2.250   0.0780   0.02370   0.01642  -0.0655   0.7518   0.8017
  -2.000   0.0800   0.02423   0.01685  -0.0606   0.7470   0.8364
  -1.750   0.0991   0.02464   0.01712  -0.0581   0.7445   0.8643
  -1.500   0.1269   0.02493   0.01725  -0.0571   0.7427   0.8869
  -1.250   0.1623   0.02541   0.01761  -0.0581   0.7399   0.9054
  -1.000   0.2661   0.02542   0.01735  -0.0713   0.7418   0.9268
  -0.750   0.3072   0.02604   0.01791  -0.0747   0.7364   0.9432
  -0.500   0.3662   0.02602   0.01777  -0.0810   0.7341   0.9531
  -0.250   0.4032   0.02595   0.01761  -0.0832   0.7311   0.9597
   0.000   0.4391   0.02577   0.01732  -0.0851   0.7288   0.9630
   0.250   0.4729   0.02550   0.01696  -0.0863   0.7269   0.9662
   0.500   0.4839   0.02617   0.01765  -0.0846   0.7190   0.9719
   0.750   0.5147   0.02610   0.01753  -0.0857   0.7155   0.9747
   1.000   0.5475   0.02586   0.01722  -0.0868   0.7130   0.9771
   1.250   0.5805   0.02555   0.01686  -0.0878   0.7111   0.9792
   1.500   0.5872   0.02645   0.01780  -0.0855   0.7018   0.9844
   1.750   0.6187   0.02625   0.01757  -0.0865   0.6989   0.9863
   2.000   0.6525   0.02590   0.01720  -0.0876   0.6967   0.9879
   2.500   0.6889   0.02658   0.01793  -0.0858   0.6842   0.9944
   2.750   0.7229   0.02621   0.01755  -0.0869   0.6819   0.9958
   3.250   0.7523   0.02686   0.01827  -0.0837   0.6687   1.0000
   3.500   0.7807   0.02645   0.01786  -0.0835   0.6664   1.0000
   4.000   0.7850   0.02716   0.01864  -0.0753   0.6521   1.0000
   4.500   0.7799   0.02776   0.01928  -0.0653   0.6373   1.0000
   5.000   0.7766   0.02833   0.01989  -0.0559   0.6222   1.0000
   5.500   0.7564   0.02970   0.02131  -0.0448   0.6018   1.0000
   6.000   0.7932   0.02900   0.02067  -0.0410   0.5921   1.0000
   6.250   0.7816   0.02992   0.02161  -0.0357   0.5800   1.0000
   6.500   0.8108   0.02916   0.02089  -0.0352   0.5771   1.0000
   6.750   0.8058   0.03007   0.02185  -0.0310   0.5651   1.0000
   7.000   0.8379   0.02925   0.02107  -0.0309   0.5620   1.0000
   7.500   0.8621   0.02993   0.02185  -0.0270   0.5433   1.0000
   7.750   0.8807   0.02999   0.02199  -0.0258   0.5345   1.0000
   8.000   0.8971   0.03028   0.02233  -0.0246   0.5250   1.0000
   8.250   0.9271   0.02972   0.02184  -0.0244   0.5182   1.0000
   8.500   0.9416   0.03020   0.02239  -0.0231   0.5070   1.0000
   8.750   0.9714   0.02972   0.02198  -0.0230   0.4988   1.0000
   9.000   0.9930   0.02979   0.02210  -0.0222   0.4880   1.0000
   9.250   1.0102   0.03017   0.02256  -0.0212   0.4759   1.0000
   9.500   1.0318   0.03029   0.02274  -0.0205   0.4640   1.0000
   9.750   1.0553   0.03030   0.02279  -0.0199   0.4518   1.0000
  10.000   1.0764   0.03047   0.02299  -0.0192   0.4384   1.0000
  10.250   1.0950   0.03082   0.02337  -0.0183   0.4244   1.0000
  10.500   1.1094   0.03145   0.02404  -0.0171   0.4095   1.0000
  11.000   1.1298   0.03328   0.02593  -0.0142   0.3771   1.0000
  11.250   1.1359   0.03449   0.02716  -0.0125   0.3594   1.0000
  11.500   1.1410   0.03580   0.02848  -0.0109   0.3407   1.0000
  11.750   1.1454   0.03719   0.02987  -0.0093   0.3214   1.0000
  12.000   1.1485   0.03874   0.03137  -0.0077   0.3014   1.0000
  12.250   1.1498   0.04054   0.03317  -0.0062   0.2807   1.0000
  12.500   1.1504   0.04246   0.03504  -0.0048   0.2598   1.0000
  12.750   1.1502   0.04457   0.03710  -0.0036   0.2386   1.0000
  13.000   1.1490   0.04687   0.03935  -0.0024   0.2175   1.0000
  13.250   1.1466   0.04937   0.04178  -0.0014   0.1968   1.0000
  13.500   1.1437   0.05207   0.04443  -0.0005   0.1753   1.0000
  13.750   1.1393   0.05503   0.04731   0.0002   0.1555   1.0000
  14.000   1.1358   0.05803   0.05030   0.0007   0.1354   1.0000
  14.250   1.1305   0.06134   0.05354   0.0011   0.1173   1.0000
  14.500   1.1247   0.06484   0.05699   0.0013   0.1014   1.0000
  14.750   1.1194   0.06839   0.06052   0.0013   0.0866   1.0000
  15.000   1.1135   0.07215   0.06426   0.0011   0.0745   1.0000
  15.250   1.1068   0.07612   0.06822   0.0008   0.0652   1.0000
  15.500   1.1022   0.07995   0.07210   0.0003   0.0575   1.0000
  15.750   1.0966   0.08399   0.07618  -0.0003   0.0514   1.0000
  16.000   1.0913   0.08810   0.08034  -0.0011   0.0469   1.0000
  16.250   1.0863   0.09223   0.08455  -0.0021   0.0429   1.0000
  16.500   1.0827   0.09626   0.08868  -0.0031   0.0396   1.0000
  16.750   1.0760   0.10079   0.09322  -0.0044   0.0370   1.0000
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